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By NASA
4 Min Read Stay Cool: NASA Tests Innovative Technique for Super Cold Fuel Storage
The tank for NASA’s two-stage cooling tests is lowered into a vacuum chamber in Test Stand 300 at NASA’s Marshall Space Flight Center in Huntsville, Alabama. Credits: NASA/Kathy Henkel In the vacuum of space, where temperatures can plunge to minus 455 degrees Fahrenheit, it might seem like keeping things cold would be easy. But the reality is more complex for preserving ultra-cold fluid propellants – or fuel – that can easily overheat from onboard systems, solar radiation, and spacecraft exhaust. The solution is a method called cryogenic fluid management, a suite of technologies that stores, transfers, and measures super cold fluids for the surface of the Moon, Mars, and future long-duration spaceflight missions.
Super cold, or cryogenic, fluids like liquid hydrogen and liquid oxygen are the most common propellants for space exploration. Despite its chilling environment, space has a “hot” effect on these propellants because of their low boiling points – about minus 424 degrees Fahrenheit for liquid hydrogen and about minus 298 for liquid oxygen – putting them at risk of boiloff.
In a first-of-its-kind demonstration, teams at NASA’s Marshall Space Flight Center in Huntsville, Alabama, are testing an innovative approach to achieve zero boiloff storage of liquid hydrogen using two stages of active cooling which could prevent the loss of valuable propellant.
“Technologies for reducing propellant loss must be implemented for successful long-duration missions to deep space like the Moon and Mars,” said Kathy Henkel, acting manager of NASA’s Cryogenic Fluid Management Portfolio Project, based at NASA Marshall. “Two-stage cooling prevents propellant loss and successfully allows for long-term storage of propellants whether in transit or on the surface of a planetary body.”
The new technique, known as “tube on tank” cooling, integrates two cryocoolers, or cooling devices, to keep propellant cold and thwart multiple heat sources. Helium, chilled to about minus 424 degrees Fahrenheit, circulates through tubes attached to the outer wall of the propellant tank.
NASA’s two-stage cooling testing setup sits in a vacuum chamber in Test Stand 300 at NASA’s Marshall Space Flight Center in Huntsville, Alabama. NASA/Tom Perrin The tank for NASA’s two-stage cooling tests is lowered into a vacuum chamber in Test Stand 300 at NASA’s Marshall Space Flight Center in Huntsville, Alabama.NASA/Kathy Henkel The tank for NASA’s two-stage cooling tests is lowered into a vacuum chamber in Test Stand 300 at NASA’s Marshall Space Flight Center in Huntsville, Alabama. NASA/Kathy Henkel The tank for NASA’s two-stage cooling tests is lowered into a vacuum chamber in Test Stand 300 at NASA’s Marshall Space Flight Center in Huntsville, Alabama. NASA/Kathy Henkel Teams installed the propellant tank in a test stand at NASA Marshall in early June, and the 90-day test campaign is scheduled to conclude in September. The tank is wrapped in a multi-layer insulation blanket that includes a thin aluminum heat shield fitted between layers. A second set of tubes, carrying helium at about minus 298 Fahrenheit, is integrated into the shield. This intermediate cooling layer intercepts and rejects incoming heat before it reaches the tank, easing the heat load on the tube-on-tank system.
To prevent dangerous pressure buildup in the propellant tank in current spaceflight systems, boiloff vapors must be vented, resulting in the loss of valuable fuel. Eliminating such propellant losses is crucial to the success of NASA’s most ambitious missions, including future crewed journeys to Mars, which will require storing large amounts of cryogenic propellant in space for months or even years. So far, cryogenic fuels have only been used for missions lasting less than a week.
“To go to Mars and have a sustainable presence, you need to preserve cryogens for use as rocket or lander return propellant,” Henkel said. “Rockets currently control their propellant through margin, where larger tanks are designed to hold more propellant than what is needed for a mission. Propellant loss isn’t an issue with short trips because the loss is factored into this margin. But, human exploration missions to Mars or longer stays at the Moon will require a different approach because of the very large tanks that would be needed.”
The Cryogenic Fluid Management Portfolio Project is a cross-agency team based at NASA Marshall and the agency’s Glenn Research Center in Cleveland. The cryogenic portfolio’s work is under NASA’s Technology Demonstration Missions Program, part of NASA’s Space Technology Mission Directorate, and is comprised of more than 20 individual technology development activities.
Learn more about cryogenic fluid management:
https://go.nasa.gov/cfm
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Last Updated Jul 18, 2025 EditorLee MohonContactCorinne M. Beckingercorinne.m.beckinger@nasa.govLocationMarshall Space Flight Center Related Terms
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Artist concept highlighting the novel approach proposed by the 2025 NIAC awarded selection of Photophoretic Propulsion Enabling Mesosphere Exploration concept.NASA/Igor Bargatin Igor Bargatin
University of Pennsylvania
We propose to use the photophoretic levitation and propulsion mechanism to create no-moving-parts flying vehicles that can be used to explore Earth’s upper atmosphere. The photophoretic force arises when a solid is heated relative to the ambient gas through illumination, inducing momentum exchange between the solid and the gas. The force creates lift in structures that absorb light on the bottom yet stay cool on the top, and we engineered our plate mechanical metamaterials to maximize this lift force and payload. The levitation and payload capabilities of our plates typically peak at ambient pressures in the 0.1-1000 Pa range, ideal for applications in Earth’s mesosphere and Mars’s low gravity and thin atmosphere. For example, in the Earth’s mesosphere (i.e., at altitudes from ~50 to ~80 km), the air is too thin for conventional airplanes or balloons but too thick for satellites, such that measurements can be performed for only a few minutes at a time during the short flight of a research rocket. However, the range of ambient pressures in the mesosphere (1-100 Pa) is nearly optimal for our plates’ payload capabilities. Phase 2 of the proposal focuses on the scalable fabrication of Knudsen pump structures that will enable missions with kg-scale payloads in the mesosphere as well as trajectory control with 1 m/s velocity control in existing stratospheric balloon vehicles.
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This project will demonstrate a fusion propulsion system based on z-pinch which is a method of compressing plasma by running electrical current though it. The z-pinch will compress and heat the plasma to produce fusion reactions, and the system will be paired with an electromagnetic accelerator to produce thrust from these reactions. The effort intends to design, build, and test a prototype device and use computational modeling to evaluate the potential performance of larger systems which would be suitable for powering deep-space missions.
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